Nickel-based superalloy and articles

ABSTRACT

A nickel-based superalloy composition includes from about 5 to about 7 wt % aluminum, from about 4 to about 8 wt % tantalum, from about 3 to about 8 wt % chromium, from about 3 to about 7 wt % tungsten, from 1 to about 5 wt % molybdenum, from 1.5 to about 5 wt % rhenium, from 5 to about 14 wt % cobalt, from about 0 to about 1 wt % hafnium, from about 0.01 to about 0.03 wt % carbon, from about 0.002 to about 0.006 wt % boron, and balance nickel and incidental impurities. The composition may exhibit a sustained peak low cycle fatigue life at 1800° F./45 ksi of at least about 4000 cycles. The nickel-based superalloy composition may be used in single-crystal or directionally solidified superalloy articles, such as a blade, nozzle, a shroud, a splash plate, and a combustor of a gas turbine engine.

CROSS REFERENCE TO RELATED APPLICATIONS

This is a division patent application of U.S. patent application Ser.No. 13/665,280, now U.S. Pat. No. 8,858,876, filed Oct. 31, 2012, thecontents of which are incorporated herein by reference.

BACKGROUND OF THE INVENTION

This invention relates generally to compositions of matter suitable foruse in aggressive, high-temperature gas turbine environments, andarticles made therefrom.

Nickel-based single crystal superalloys are used extensively throughoutthe aeroengine in turbine blade, nozzle, and shroud applications.Aeroengine designs for improved engine performance demand alloys withincreasingly higher temperature capability, primarily in the form ofimproved creep strength (creep resistance). Alloys with increasedamounts of solid solution strengthening elements such as Ta, W, Re, andMo, which also provide improved creep resistance, generally exhibitdecreased phase stability, increased density, and lower environmentalresistance. Recently, thermal-mechanical fatigue (TMF) resistance hasbeen a limiting design criterion for turbine components. Temperaturegradients create cyclic thermally induced strains that promote damage bya complex combination of creep, fatigue, and oxidation. Directionallysolidified superalloys have not historically been developed for cyclicdamage resistance. However, increased cyclic damage resistance isdesired for improved engine efficiency.

Single crystal superalloys may be classified into four generations basedon similarities in alloy compositions and high temperature mechanicalproperties. So-called first generation single crystal superalloyscontain no rhenium. Second generation superalloys typically containabout three weight percent rhenium. Third generation superalloys aredesigned to increase the temperature capability and creep resistance byraising the refractory metal content and lowering the chromium level.Exemplary alloys have rhenium levels of about 5.5 weight percent andchromium levels in the 2-4 weight percent range. Fourth and fifthgeneration alloys include increased levels of rhenium and otherrefractory metals, such as ruthenium.

Second generation alloys are not exceptionally strong, although theyhave relatively stable microstructures. Third and fourth generationalloys have improved strength due to the addition of high levels ofrefractory metals. For example, these alloys include high levels oftungsten, rhenium, and ruthenium. These refractory metals have densitiesthat are much higher than that of the nickel base, so their additionincreases the overall alloy density. For example, fourth generationalloys may be about 6% heavier than second generation alloys. Theincreased weight and cost of these alloys limit their use to onlyspecialized applications. Third and fourth generation alloys are alsolimited by microstructural instabilities, which can impact long-termmechanical properties.

Each subsequent generation of alloys was developed in an effort toimprove the creep strength and temperature capability of the priorgeneration. For example, third generation superalloys provide a 50° F.(about 28° C.) improvement in creep capability relative to secondgeneration superalloys. Fourth and fifth generation superalloys offer afurther improvement in creep strength achieved by high levels of solidsolution strengthening elements such as rhenium, tungsten, tantalum,molybdenum and the addition of ruthenium.

As the creep capability of directionally solidified superalloys hasimproved over the generations, the continuous-cycle fatigue resistanceand the hold-time cyclic damage resistance have also improved. Theseimprovements in rupture and fatigue strength have been accompanied by anincrease in alloy density and cost, as noted above. In addition, thereis a microstructural and environmental penalty for continuing toincrease the amount of refractory elements in directionally solidifiedsuperalloys. For example, third generation superalloys are less stablewith respect to topological close-packed phases (TCP) and tend to form asecondary reaction zone (SRZ). The lower levels of chromium, necessaryto maintain sufficient microstructural stability, results in decreasedenvironmental resistance in the subsequent generations of superalloys.

Cyclic damage resistance is quantified by hold time or sustained-peaklow cycle fatigue (SPLCF) testing, which is an important propertyrequirement for single crystal turbine blade alloys. The third andfourth generation single crystal superalloys have the disadvantages ofhigh density, high cost due to the presence of rhenium and ruthenium,microstructural instability under coated condition (SRZ formation), andinadequate SPLCF lives.

Accordingly, it is desirable to provide single crystal superalloycompositions that contain less rhenium and ruthenium, have longer SPLCFlives, and have improved microstructural stability through less SRZformation, while maintaining adequate creep and oxidation resistance.

BRIEF DESCRIPTION OF THE INVENTION

Fatigue resistant nickel-based single crystal superalloys for turbineblade applications that provide lower density, low rhenium and rutheniumcontent, low cost, improved SPLCF resistance, and less SRZ formationcompared to known alloys as well as balanced creep and oxidationresistance are described in various exemplary embodiments.

According to an exemplary embodiment, a composition of matter comprisesfrom about 5 to about 7 wt % aluminum, from about 4 to about 8 wt %tantalum, from about 3 to about 8 wt % chromium, from about 3 to about 7wt % tungsten, from 1 to about 5 wt % molybdenum, from 1.5 to about 5 wt% rhenium, from 5 to about 14 wt % cobalt, from about 0 to about 1 wt %hafnium, from about 0.01 to about 0.03 wt % carbon, from about 0.002 toabout 0.006 wt % boron, and balance nickel and incidental impurities.According to embodiments of the invention, the composition may exhibit asustained peak low cycle fatigue life at 1800° F./45 ksi of at leastabout 4000 cycles.

Exemplary embodiments disclosed herein include an article, such as ablade, nozzle, a shroud, a splash plate, and a combustor of a gasturbine engine, comprising a substantially single crystal having acomposition comprising from about 5 to about 7 wt % aluminum, from about4 to about 8 wt % tantalum, from about 3 to about 8 wt % chromium, fromabout 3 to about 7 wt % tungsten, from 1 to about 5 wt % molybdenum,from 1.5 to about 5 wt % rhenium, from 5 to about 14 wt % cobalt, fromabout 0 to about 1 wt % hafnium, from about 0.01 to about 0.03 wt %carbon, from about 0.002 to about 0.006 wt % boron, and balance nickeland incidental impurities. According to embodiments of the invention,the composition may exhibit a sustained peak low cycle fatigue life at1800° F./45 ksi of at least about 4000 cycles.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter which is regarded as the invention is particularlypointed out and distinctly claimed in the concluding part of thespecification. The invention, however, may be best understood byreference to the following description taken in conjunction with theaccompanying drawing figures in which:

FIG. 1 is a perspective view of an article, such as a gas turbine blade,according to an embodiment of the invention.

FIG. 2 is a table setting forth exemplary compositions according to theinvention and reference compositions.

FIG. 3 is a graph showing sustained peak low cycle fatigue life (SPLCF)(cycles) at 1800° F./45 ksi as a function of total Re and Ruconcentration (wt %) for exemplary compositions according to theinvention and reference compositions.

FIG. 4 is a graph showing rupture tolerance (hours) at 2000° F./20 ksias a function of total Re and Ru concentration (wt %) for exemplarycompositions according to the invention and reference compositions.

FIG. 5 is a block-flow diagram illustrating an approach for preparing anarticle according to the invention.

DETAILED DESCRIPTION OF THE INVENTION

This invention describes the chemistries of Ni-based single crystalsuperalloys for turbine blade applications. The superalloys providelower density, low rhenium and ruthenium content, low cost, improvedSPLCF resistance, and less SRZ formation compared to known alloys, aswell as balanced creep and oxidation resistance. The improvement offatigue resistance was achieved by balancing the strength, oxidation andcreep resistance of the alloys through controlling the amount of gammastrengtheners such as W, Mo, Re, Co and Cr and by controlling the volumefraction of gamma prime phase by controlling the concentration of Al,Ta, Hf. The invention is described in various exemplary embodiments.

Referring to the drawings, FIG. 1 depicts a component of a gas turbineengine, illustrated as a gas turbine blade 10. The gas turbine blade 10includes an airfoil 12, a laterally extending platform 16, an attachment14 in the form of a dovetail to attach the gas turbine blade 10 to aturbine disk (not shown). In some components, a number of coolingchannels extend through the interior of the airfoil 12, ending inopenings 18 in the surface of the airfoil 12.

In an exemplary embodiment, the component article 10 is substantially asingle crystal. That is, the component article 10 is at least about 80percent by volume, and more preferably at least about 95 percent byvolume, a single grain with a single crystallographic orientation. Theremay be minor volume fractions of other crystallographic orientations andalso regions separated by low-angle boundaries. The single-crystalstructure is prepared by the directional solidification of an alloycomposition, usually from a seed or other structure that induces thegrowth of the single crystal and single grain orientation.

The use of exemplary alloy compositions discussed herein is not limitedto the gas turbine blade 10, and it may be employed in other articlessuch as gas turbine nozzles, vanes, shrouds, or other components for gasturbine engines.

It is believed that the exemplary embodiments disclosed herein provide aunique alloying approach for improved SPLCF and rupture resistantalloys. Table I below provides exemplary concentration ranges in weightpercent for the elements included in the alloy of the invention. Allamounts provided as ranges, for each element, should be construed toinclude endpoints and sub-ranges.

TABLE I Exemplary Concentration Ranges Alloy Al Ta Cr W Mo Re Co Hf C BNi Min. 5 4 3 3 1 1.5 5 0 0.01 0.002 Bal. wt % Max. 7 8 8 7 5 5 14 10.03 0.006 Bal. wt %

Exemplary embodiments disclosed herein may include aluminum to provideimproved SPLCF resistance and oxidation resistance. Exemplaryembodiments may include from about 5 to about 7 wt % aluminum. Otherexemplary embodiments may include from about 5.5 to about 6.5 wt %aluminum. Other exemplary embodiments may include from about 5.5 toabout 6.2 wt % aluminum. Other exemplary embodiments may include fromabout 6.1 to about 6.5 wt % aluminum. Other exemplary embodiments mayinclude from about 6.2 to about 6.4 wt % aluminum.

Exemplary embodiments disclosed herein may include tantalum to promotegamma prime strength. Exemplary embodiments may include from about 4 toabout 8 wt % tantalum. Other exemplary embodiments may include fromabout 4.5 to about 8 wt % tantalum. Other exemplary embodiments mayinclude from about 6 to about 8 wt % tantalum. Other exemplaryembodiments may include from about 4 to about 6 wt % tantalum.

Exemplary embodiments disclosed herein may include chromium to improvehot corrosion resistance. Exemplary embodiments may include from about 3to about 8 wt % chromium. Other exemplary embodiments may include fromabout 4 to about 6.5 wt % chromium. Other exemplary embodiments mayinclude from about 4.3 to about 6.5 wt % chromium. Other exemplaryembodiments disclosed herein may include from about 4.5 to about 5 wt %chromium. Other exemplary embodiments may include from about 5 to about6.5 wt % chromium. Other exemplary embodiments disclosed herein mayinclude from about 5.5 to about 6 wt % chromium.

Exemplary embodiments disclosed herein may include tungsten as astrengthener. Exemplary embodiments may include from about 3 to about 7wt % tungsten. Other exemplary embodiments may include tungsten inamounts from about 3 to about 6 wt %. Other exemplary embodiments mayinclude tungsten in amounts from about 4 to about 6 wt %. Otherexemplary embodiments may include tungsten in amounts from about 3.5 toabout 6.5 wt %. Other exemplary embodiments may include tungsten inamounts from about 3.5 to about 6 wt %.

Exemplary embodiments disclosed herein may include molybdenum to impartsolid solution strengthening. Exemplary embodiments may include fromabout 1 to about 5 wt % molybdenum. Other exemplary embodiments mayinclude molybdenum in amounts from about 2 to about 5 wt %. Otherexemplary embodiments may include molybdenum in amounts from about 2 toabout 4 wt %. Other exemplary embodiments may include molybdenum inamounts from about 2 to about 3 wt %. Other exemplary embodiments mayinclude molybdenum in amounts from about 1.5 to about 4 wt %. Otherexemplary embodiments may include molybdenum in amounts from about 1.5to about 2.5 wt %.

Exemplary embodiments disclosed herein may include rhenium, which is apotent solid solution strengthener that partitions to the gamma phase,and also is a slow diffusing element, which limits coarsening of thegamma prime. Exemplary embodiments may include from about 1.5 to about 5wt % rhenium. Other exemplary embodiments may include rhenium at levelsbetween about 2.5 to about 4.5 wt %. Other exemplary embodiments mayinclude rhenium at levels between about 3 to about 4.2 wt %. Otherexemplary embodiments may include rhenium at levels between about 3 toabout 4 wt %. Other exemplary embodiments may include rhenium at levelsbetween about 2.5 to about 4.5 wt %. Other exemplary embodiments mayinclude rhenium at levels between about 3.5 to about 4.2 wt %.

Exemplary embodiments disclosed herein may include cobalt. Exemplaryembodiments may include from about 5 to about 14 wt % cobalt. Otherexemplary embodiments may include from about 7 to about 12.5 wt %cobalt. Other exemplary embodiments may include from about 9 to about 12wt % cobalt. Other exemplary embodiments may include from about 5 toabout 8 wt % cobalt. Other exemplary embodiments may include from about6.5 to about 7.5 wt % cobalt.

Exemplary embodiments disclosed herein may optionally include hafnium,which improves the oxidation and hot corrosion resistance of coatedalloys. Hafnium may improve the life of thermal barrier coatings.Exemplary embodiments may include from about 0 to about 1 wt % hafnium.Other exemplary embodiments may include from about 0.2 to about 0.6 wt %hafnium.

Exemplary embodiments disclosed herein may include carbon. Exemplaryembodiments may include from about 0.01 to about 0.03 wt % carbon. Otherexemplary embodiments may include from about 0.015 to about 0.025 wt %carbon. Other exemplary embodiments may include from about 0.015 toabout 0.025 wt % carbon.

Exemplary embodiments disclosed herein may include boron to providetolerance for low angle boundaries. Exemplary embodiments may includefrom about 0.002 to about 0.006 wt % boron. Other exemplary embodimentsmay include from about 0.0025 to about 0.0055 wt % boron. Otherexemplary embodiments may include from about 0.003 to about 0.005 wt %boron. Other exemplary embodiments may include from about 0.0035 toabout 0.0045% boron.

According to an exemplary embodiment, a composition of matter comprisesfrom about 5 to about 7 wt % aluminum, from about 4 to about 8 wt %tantalum, from about 3 to about 8 wt % chromium, from about 3 to about 7wt % tungsten, from 1 to about 5 wt % molybdenum, from 1.5 to about 5 wt% rhenium, from 5 to about 14 wt % cobalt, from about 0 to about 1 wt %hafnium, from about 0.01 to about 0.03 wt % carbon, from about 0.002 toabout 0.006 wt % boron, and balance nickel and incidental impurities.

In another embodiment, a composition of matter comprises from about 5.5to about 6.5 wt % aluminum, from about 4.5 to about 8 wt % tantalum,from about 4 to about 6.5 wt % chromium, from about 3 to about 6 wt %tungsten, from 2 to about 5 wt % molybdenum, from 2.5 to about 4.5 wt %rhenium, from 7 to about 12.5 wt % cobalt, from about 0.2 to about 0.6wt % hafnium, from about 0.015 to about 0.025 wt % carbon, from about0.0025 to about 0.0055 wt % boron, and balance nickel and incidentalimpurities.

In yet another embodiment, a composition of matter comprises from about5.5 to about 6.5 wt % aluminum, from about 6 to about 8 wt % tantalum,from about 4.3 to about 6.5 wt % chromium, from about 4 to about 6 wt %tungsten, from 2 to about 4 wt % molybdenum, from 3 to about 4.2 wt %rhenium, from 7 to about 12.5 wt % cobalt, from about 0.2 to about 0.6wt % hafnium, from about 0.015 to about 0.025 wt % carbon, from about0.003 to about 0.005 wt % boron, and balance nickel and incidentalimpurities.

In another embodiment, a composition of matter comprises from about 5.5to about 6.2 wt % aluminum, from about 6 to about 8 wt % tantalum, fromabout 4.5 to about 5 wt % chromium, from about 4 to about 6 wt %tungsten, from 2 to about 3 wt % molybdenum, from 3 to about 4 wt %rhenium, from 9 to about 12.0 wt % cobalt, from about 0.2 to about 0.6wt % hafnium, from about 0.015 to about 0.025 wt % carbon, from about0.0035 to about 0.0045 wt % boron, and balance nickel and incidentalimpurities.

In yet another embodiment, a composition of matter comprises from about6.1 to about 6.5 wt % aluminum, from about 4 to about 6 wt % tantalum,from about 5 to about 6.5 wt % chromium, from about 3.5 to about 6.5 wt% tungsten, from 1.5 to about 4 wt % molybdenum, from 2.5 to about 4.5wt % rhenium, from 5 to about 8 wt % cobalt, from about 0.2 to about 0.6wt % hafnium, from about 0.015 to about 0.025 wt % carbon, from about0.003 to about 0.005 wt % boron, and balance nickel and incidentalimpurities.

In another embodiment, a composition of matter comprises from about 6.2to about 6.4 wt % aluminum, from about 4 to about 6 wt % tantalum, fromabout 5.5 to about 6 wt % chromium, from about 3.5 to about 6 wt %tungsten, from 1.5 to about 2.5 wt % molybdenum, from 3.5 to about 4.2wt % rhenium, from 6.5 to about 7.5 wt % cobalt, from about 0.2 to about0.6 wt % hafnium, from about 0.015 to about 0.025 wt % carbon, fromabout 0.0035 to about 0.0045 wt % boron, and balance nickel andincidental impurities.

Exemplary embodiments disclosed herein include an article, such as ablade, nozzle, a shroud, a splash plate, and a combustor of a gasturbine engine, comprising a substantially single crystal having acomposition comprising from about 5 to about 7 wt % aluminum, from about4 to about 8 wt % tantalum, from about 3 to about 8 wt % chromium, fromabout 3 to about 7 wt % tungsten, from 1 to about 5 wt % molybdenum,from 1.5 to about 5 wt % rhenium, from 5 to about 14 wt % cobalt, fromabout 0 to about 1 wt % hafnium, from about 0.01 to about 0.03 wt %carbon, from about 0.002 to about 0.006 wt % boron, and balance nickeland incidental impurities.

Exemplary compositions according to the invention and referencecompositions are presented in the FIG. 2. As indicated in FIG. 2, alloysA1-A6 have compositions according to the invention. Reference alloysR1-R5 have compositions that fall outside of the compositional rangesaccording to the invention, as described above. FIG. 2 also provides thesustained-peak low cycle fatigue resistance (SPLCF) (cycles) at 1800°F./45 ksi and rupture life at 2000° F./20 ksi (hours) for alloys A1-A6as well as reference alloys R1-R5.

The SPLCF testing was performed by applying strain controlled,compressive hold for 2 minutes at 1800° F. with an alternate pseudostress of 45 ksi.

As indicated in FIG. 2, the alloys A1, A5, and A6 have SPLCF and rupturetolerances greater than reference alloys R1-R5. In general, the alloysaccording to an embodiment of the invention exhibit a SPLCF greater thanabout 4000 cycles at 1800° F./45 ksi and a rupture of greater than about150 hours at 2000° F./20 ksi. Specifically, alloy A1 has a SPLCF ofabout 4111 cycles and a rupture life of about 155 hours. Further, thealloys according to another embodiment of the invention generallyexhibit a SPLCF greater than about 5000 cycles at 1800° F./45 ksi and arupture life of greater than about 200 hours at 2000° F./20 ksi. Inparticular, A5 has a SPLCF of about 5497 cycles and a rupture life ofabout 203 hours, and alloy A6 has a SPLCF of about 5219 cycles and arupture life of about 211 hours.

FIG. 3 is a graph showing SPLCF life (cycles) at 1800° F./45 ksi as afunction of total Re and Ru concentration (wt %) for exemplarycompositions according to the invention and reference compositions. FIG.4 is a graph showing rupture life (hours) at 2000° F./20 ksi as afunction of total Re and Ru concentration (wt %) for exemplarycompositions according to the invention and reference compositions.

As indicated in FIGS. 3 and 4, alloys A1, A5, and A6 according to theinvention have much higher SPLCF and rupture lives than the referencealloys R1-R5 with similar or higher Re+Ru concentrations. In particular,alloys A1 and A5 have a Re+Ru concentration of about 4 wt %, and alloyA6 has a Re+Ru concentration of about 3.5 wt %. Reference alloys R3-R5have higher Re+Ru concentrations than alloys A1, A5, and A6, but exhibitlower SPLCF and rupture lives than alloys A1, A5, and A6.

The data summarized in FIGS. 2-4 indicates that the exemplaryembodiments disclosed herein demonstrate an improved combination offatigue and creep resistance than known alloys. In addition, anadvantage of the alloys of the invention is that their relatively lowtotal concentration of rhenium and ruthenium, as compared to some of thereference alloys, significantly reduces the cost of the alloys.

The exemplary embodiments describe the compositions and somecharacteristics of the alloys, but should not be interpreted as limitingthe invention in any respect.

FIG. 5 is a block-flow diagram illustrating an approach for preparing anarticle according to the invention. An alloy having the composition setforth above is prepared, as shown at reference numeral 20. The alloy ismelted and solidified as substantially a single crystal, as shown atreference numeral 22. Techniques for solidifying single crystal articlesare well-known in the art. Generally, they involve solidifying the alloyin a mold unidirectionally from one end of the article, with a seed orgrowth constriction defining the single crystal orientation that isdesired in the article. In most cases, the article is prepared with a[001] crystallographic direction parallel to a long axis of the articlein the case of the turbine blade or turbine vane. After solidificationas a single crystal, the article is post processed by any operabletechnique, as shown at reference numeral 24. Post processing mayinclude, but is not limited to heat treating the article to optimize themechanical properties of the alloy and/or machining the article.

This written description uses exemplary embodiments to disclose theinvention, including the best mode, and also to enable any personskilled in the art to make and use the invention. The patentable scopeof the invention is defined by the claims, and may include otherexemplary embodiments that occur to those skilled in the art. Such otherexemplary embodiments are intended to be within the scope of the claimsif they have structural elements that do not differ from the literallanguage of the claims, or if they include equivalent structuralelements with insubstantial differences from the literal languages ofthe claims.

What is claimed is:
 1. A composition of matter, comprising: from about 5to about 7 wt % aluminum; from about 5.5 to about 8 wt % tantalum; about4.3 wt % chromium; from about 3.5 to about 7 wt % tungsten; from 1.5 toabout 2.5 wt % molybdenum; from 3 to about 4 wt % rhenium; from 9 toabout 12 wt % cobalt; from about 0.2 to about 0.6 wt % hafnium; fromabout 0.01 to about 0.03 wt % carbon; from about 0.002 to about 0.006 wt% boron; and balance nickel and incidental impurities, wherein thecomposition exhibits a sustained peak low cycle fatigue life at 1800°F./45 ksi of at least 4000 cycles.
 2. The composition of matter of claim1, wherein the composition of matter comprises from about 6 to about 8.0wt % tantalum, from about 4.0 to about 6.0 wt % tungsten, from about 2.0to about 2.5 wt % molybdenum, and from about 3.5 to 4.0 wt % rhenium. 3.The composition of matter of claim 1, wherein the composition of mattercomprises from about 6.5 to about 8 wt % tantalum and from about 5 toabout 6 wt % tungsten.
 4. The composition of matter of claim 1, whereinthe composition of matter does not comprise ruthenium.
 5. Thecomposition of matter of claim 1, wherein the composition of mattercomprises a combined total content of tantalum, molybdenum, and rheniumof less than 14.5 wt %.
 6. An article comprising the composition ofmatter of claim
 1. 7. The composition of matter of claim 1, wherein thecomposition exhibits a sustained peak low cycle fatigue life at 1800°F./45 ksi of at least 5000 cycles.
 8. The composition of matter of claim1, wherein the composition exhibits a rupture life at 2000° F./20 ksi ofat least 150 hours.
 9. The composition of matter of claim 1, wherein thecomposition exhibits a rupture life at 2000° F./20 ksi of at least 200hours.
 10. An article comprising a composition comprising: from about 5to about 7 wt % aluminum; from about 5.5 to about 8 wt % tantalum; about4.3 wt % chromium; from about 3.5 to about 7 wt % tungsten; from 1.5 toabout 2.5 wt % molybdenum; from 3 to about 4 wt % rhenium; from 9 toabout 12 wt % cobalt; from about 0.2 to about 0.6 wt % hafnium; fromabout 0.01 to about 0.03 wt % carbon; from about 0.002 to about 0.006 wt% boron; and balance nickel and incidental impurities, wherein thecomposition exhibits a sustained peak low cycle fatigue life at 1800°F./45 ksi of at least 4000 cycles.
 11. The article of claim 10, whereinthe article comprises a component of a gas turbine engine selected froma nozzle, a shroud, a splash plate, and a combustor component.
 12. Thearticle of claim 10, wherein the article comprises a directionallysolidified component.
 13. The article of claim 10, wherein the articlecomprises a single-crystal component.
 14. The article of claim 13,wherein the single-crystal component comprises a blade of a gas turbine.15. The article of claim 12, wherein the directionally solidifiedcomponent comprises a blade of a gas turbine.
 16. A composition ofmatter, consisting of: from about 5 to about 7 wt % aluminum; from about5.5 to about 8 wt % tantalum; about 4.3 wt % chromium; from about 3.5 toabout 7 wt % tungsten; from 1.5 to about 2.5 wt % molybdenum; from 3 toabout 4 wt % rhenium; from 9 to about 12 wt % cobalt; from about 0.2 toabout 0.6 wt % hafnium; from about 0.01 to about 0.03 wt % carbon; fromabout 0.002 to about 0.006 wt % boron; and balance nickel and incidentalimpurities, wherein the composition exhibits a sustained peak low cyclefatigue life at 1800° F./45 ksi of at least 4000 cycles.
 17. Thecomposition of matter of claim 16, wherein the composition of matterconsists of: from about 5 to about 7 wt % aluminum; from about 6.0 toabout 8 wt % tantalum; about 4.3 wt % chromium; from about 4.0 to about7 wt % tungsten; from 2.0 to about 2.5 wt % molybdenum; from 3.5 toabout 4 wt % rhenium; from 9 to about 12 wt % cobalt; from about 0.2 toabout 0.6 wt % hafnium; from about 0.01 to about 0.03 wt % carbon; fromabout 0.002 to about 0.006 wt % boron; and balance nickel and incidentalimpurities, wherein the composition exhibits a sustained peak low cyclefatigue life at 1800° F./45 ksi of at least 4000 cycles.
 18. Thecomposition of matter of claim 16, wherein the composition of matterconsists of: from about 5 to about 7 wt % aluminum; from about 6.5 toabout 8 wt % tantalum; about 4.3 wt % chromium; from about 5 to about 6wt % tungsten; from 1.5 to about 2.5 wt % molybdenum; from 3 to about 4wt % rhenium; from 9 to about 12 wt % cobalt; from about 0.2 to about0.6 wt % hafnium; from about 0.01 to about 0.03 wt % carbon; from about0.002 to about 0.006 wt % boron; and balance nickel and incidentalimpurities, wherein the composition exhibits a sustained peak low cyclefatigue life at 1800° F./45 ksi of at least 4000 cycles.
 19. An articlecomprising the composition of matter of claim
 16. 20. The composition ofmatter of claim 16, wherein the composition exhibits a sustained peaklow cycle fatigue life at 1800° F./45 ksi of at least 5000 cycles. 21.The composition of matter of claim 16, wherein the composition exhibitsa rupture life at 2000° F./20 ksi of at least 150 hours.
 22. Thecomposition of matter of claim 16, wherein the composition exhibits arupture life at 2000° F./20 ksi of at least 200 hours.